Path: ACPro/ACProAerodynamics
% Optimal lift and drag coefficients for the Concorde.
Output is function of Mach number.
Type ConcordeLD for a demo
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Form:
[cL, cD, k1, k2] = ConcordeLD( m )
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Inputs
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m (1,:) Mach number
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Outputs
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cL (1,:) Lift coefficient
cD (1,:) Drag coefficient
k1 (1,:) Drag at zero lift
k2 (1,:) Drag from lift coefficient (Induced drag)
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Reference: Austyn Mair, W. and D.L.L. Birdsall (1992.)
Aircraft Performance. Cambridge. pp. 40-41 and p.261.
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Common: CommonData/SwooshWatermark Common: General/CellToMat Common: General/MatToCell Common: General/Watermark Common: Graphics/NewFig Common: Graphics/Plot2D Common: Graphics/PltStyle
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